Fuel-tank.



H. c. MOUGEY Q 1. M. HQJACOBS.

FUEL IANK. l APPLICAION FILED SEP`I|23| l9l8- Patented Mar. 25, 1919.

lilas?? MZESSES cendiary bullets,

UNITED rarnnr carica.

HARRY C. MOG-EY AND JAMES E. H, JJ'ACO-BS, OF DAYTON, OHIO, ASSIGNOBS TOTHB `DAYTON METAL PRODUCTS COMPANY, A CORPORATION OF OHIO.

FUEL-TANK.

Specication of Letters Patent.

Patented Mar. 25, 1919;

Mumien mea september 23, 191s. sei-iai no. 255,406.

To all Iwhom t may concern:

Bc it known that we, HARRY C. MOUGEY and JAMES M. H. JACOBS, citizens ofthe United States of America, residing at Dayton, county of Montgomery,State of Ohio, have invented certain new and useful Improvements inFuel-Tanks, of which the following is a full, clear, and exactdescription. i

This invention relates to fuel tanks and more particularly to animproved fuel tank especially adapted for use in airplanes.

The principal object of the invention is to provide an improved fueltank constructed to prevent, under all circumstances, the leakage offuel onto the airplane, to thus minimize, or entirely eliminate, thedanger of having the airplane set on fire by inor otherwise, duringflight.

Other objects and advantages of the inv-ention will be apparent from thedescription thereof set out below, reference being had to theaccompanying drawing in which- .Figure 1 is a fragmentary diagrammaticview, in elevation, of a typical'form of airplane containing my improvedfuel tank;

Fig. 2v is a transverse sectional view through the tank and airplanebody, illustrated in Fig. 1; and

Fig. 3 is a longitudinal sectional view of the device, with parts brokenaway to more clearly illustrate the construction.

In the drawing, in which like vcharacters of reference designate likeparts throughout the several views thereof, 10 is the body, or fuselage,of a conventional airplane having the usual wings landing gear 13. Thefuselage, 10 consists veneering 14 which is attached, in theconventionalway, to the vloiigerons 15. Any other type of covering forthe body of the fuselage may be used if desired, the precise type ofcovering being a matter of/indifference so far-as this invention isconcerned.

shell of the body, or of va thin sheetV of All the structure thus fardescribed is purely conventional.

Our improved tank erally by the numeral 20. This tank consists of amet-al tank 21 preferably composed of a soft or ductile metal,l such lascopper, adapted to contain the fuel. In order to secure themostdesirable type of tank this metal should be of some material which11, propeller 12 and is designated gen- -offers comparatively littleresist-ance to the passage of the bullet therethrough. Where a metalsuch as the steel of which fuel tanks are ordinarily made is used it isfound that when a bullet passes through the tank the hole in the side ofthe tankmade vby the bullet on entering will be clean cut and just largeenough to permit the passage of the bullet, whereas the hole in theopposite side of the tank will at times be of considerable size, andeven where it does not reach large proportions the metal surrounding thehole will often be carried along by the bullet to form outstanding,jagged projections. Where a soft or ductile metal suchas copper is usedwe have found that the hole made by the bullet on leavingtlie tank isnot substantially larger than the hole made on entering the tank. And wehave further found that there is practically no tendency for the bulletto form outstanding projections around the' exit hole made in passingthrough the metal. understood that the metal composing this tank neednot necessarily be 4copper as it may bcv an-y desired soft or ductilemetal, brass and soft steel giving very good results. Rigidly attachedto the shell of the tank are several outstanding lugs or projections 22.As shown there,A are four of these lugs or projections 22 which serve assup orts for the tank when it is mounted in t e body of the airplane.Any other supporting means desired may be used in place of these lugs.Opening into the tank through the upper end thereof is a passagev 23lclosed by the cap 24 which is adaptedl to be threaded upon the wall ofthis passage for closing the tank. -This passage 23 is the conventionalfilling opening.

Surrounding the metallic tank 21 is a covering or bag of rubber 30. Thepurpose of using rubber is to secure a covering material adapted toquickly close up anyv holes that may be formed therein. In actualpractice it has been found that if a bullet is shot through a rubbercovering of substantial thickness, `a quarter of; an inch thick forexample, the hole formed by 'such VEbullet will tend to close up,especially in the presence of a fuel such as gasolene, and will preventthe flow therethrough of any subfuel within the tank.

It is preferable that the We wish it expressly A the tank loosely. Wehave found that where the rubber covering nts the tank closely., as acoating, there is a tendency for the bullet passing through the tank totear a large hole in the coating on its way out, but that where a looserubber covering 1s used this tendency is practically eliminated.Surrounding the metallic tank 21 and its l loose rubber covering 30 is asecond rubber covering 35 which is spaced from the first rubbercovering, leaving a substantial space 31 between them. This covering, assho-wn in the drawing, consists of three parts, a lower section 36 whichcovers the lower part ofthe tank, an upper. section 37 which covers theupper part of the tank, and a top section 38 vadapted to t within theupper section, to ti htly close that section, the three sections when inplace thus forming what is in edect a one piece tank. As shown in thedrawing the projections 22 pass entirely through the -inner rubbercoverlng 30. The outer rubber covering, however, is so arranged that theupjper end of the lower section and the lower end of the upper sectionsurround these projections and overlap. Passing through the rojections22 are bolts 40 which also pass crough the over-.lapping ends of theupper and lower rubber sections 36 and 37 and through the longerons 15and the cross #beams 4l, which extend between the longe rons and serveas supports for the tank. It is obvious that tightening the bolts e0, tohold the tank securely in position within the airplane, tends to pressthe over-lapping parts of the sections 36band 37 closely ,toget-her tothus ymake a tight joint and prevent any fuel that may leak intothespace 31 from escaping therethrough onto the parts of the airplane. T-ofurther insure the prevention of leakage through this joint onto theairplane theover-lapping ends of the rubber sections are so positionedthat any fluid .flowing down the inner wall will tend to drain back intothe lspace 31 and to not escape to the outside of the tank. The

. ysole reason for making the outer covering 35 whole is adapted toprevent leakageo in sections is to permit of easier assemblage.Obviously this covering may be made in one piece, or in ahy numberofpieces, if'desired so long as, when assembled, the covering as a fueltherethrough. The lower rubber section 36 has through the bottom thereofan outlet opening 45 adapted to permit the escape ltherethrough of anyfuel that may leak into the space 31. Filling the space 31 is fibrous,

or some analogous material 32 adapted to cause any fuel that may leakinto the space to drain through such material to the bottom ofthe spacewhere it may escape through the i opening 45. In actual practice'we haveused excelsior to llthe space 31. This material need not necessarilyv beabsorbent but should be ofl such character that 'it will cause anyincenso fuel leaking into the space to drain toward the openingin thebottom of the outer covering 35.

The purpose of this construction is thought obvious from the abovedescription. The use of -a ductile metal tank prevents the bullet fromtearing big holes in such tank and further prevents it from formingjagged outstanding projections around the 4exit hole. In the `absence ofthese objectionable features the bullet as it passes through the loosefitting rubber covering 30 normally makes a hole therein no larger thanis necessary for permitting passage of the bullet. A hole of this sizeis generally quickly closed up by the rubber itself. As a resulttherefore the passage of a bullet completely through the inner tank andits inclosing rublber covering 30 will generally result in noappreciable leakage of fuel through the bullet holes, and even when suchleakage occurs only a small quantity of fuel will escape. The ductilemetal tank and its loose fitting rubber covering therefore are designedto prevent any leakage "of fuel from the tank when it is punctured by abullet. If, however, such leakage does occur the fuel is caught 'by thematerial within the space 31, which tends `to break up any streams offuel iiowing through holes in the tank 4to prevent the fuel fromescaping through the corresponding holes in the outer covering, and isdrained to the bottom of this space where it vcan escape through theopening 45. The eX- celsior or fibrous material also tends to preventthe formation of air currents through the space 31 which of itselfminimizes the danger'of any fuel within such space being ignited, as 'byan incendiary bullet.

Coperating with the opening 45 is a funnel shaped member 50 which `isheld i ace aga-inst the bottom ofthe section 36, and surrounding theopening 45 thereof, by means of a rubber' pad 51. Thispad 51 is locatedbetween the bottom of the section 36, and the funnel shaped member 50,and the bottom of the fuselage and is adapted to hold the funnel shapedmember 50 tightly `against the bottom of the lower rubber section 36'tothus prevent leakage at this point. Obviously any other desired type ofmaterial may be used .for constituting this pad, but if desired it maybe entirely dispensed with and some other desired means of connectingthe funnel shaped member tightly to the rubber section 36 may beprovided. Connected to the funnel shaped member 50 is a drain pipe 52the lower end ofwhich terminates adjacent the lowest point of thelanding gear 13. This pipe is also preferably of it too is punctured. Ithas been found in actual practice that where a drain pipe has its lower,or outlet, .end thus positioned any rubber, to minimize leakage in caseis in ight will not be sprayed upon, the

parts'of the machine, but will be diipated into the atmosphere. Andobviously while the machine is at rest none of the fuel will escapethereonto. It is not necessary that the drain pipe terminate adjacentthe lowest part` of the landing gear, although we have found thislocation the most desirable one. It is only necessary that the outletend of the drain pipe be so positioned that any fuel escapingtherethrough shall not get upon the body or other parts of' theairplane. The common practice in aerial warfare is to use incendiarybullets. If one of these bullets passes through a part of an airplanesaturated with gasolene the machine will be immediately set on fire andit is estimated that a large percentage of the fatalities in aerialwarfare, probably above 75%, result from airplanes being thus set onfire. It is obvious that the location'of'the drain pipe terminal needonly De such that it will prevent the escape of the fuel onto the partsof the airplane in case of leakage of fuel into the space 3l. A

From the above description the method of functioning of this apparatusisthought quite clear. The ductile metal tank and its loose covering, asstated above, are adapted to prevent any leakage of fuel. In case anysuch leakage should occur, however, the outer rubber covering with thematerial intermediate the two coverings is adapted to prevent the escapeof any of this leaking fuel to the outside except through the drainpipe. And the drain pipe is so arranged that any fuel that may passtherethrough will be fed into the atmosphere at such a point that noneof it will get upon the airplane or its parts. If desired the innercovering 3() may be dispensed with. Under such circumstances there willbe nothing to prevent the escape into the space 31 of fuel in case thetank is punctured, but the .outer covering and fibrous material will beaffective in catching such fuel and draining it away, without 'ismounted, being set on fire from incendiary bullets, or other causes,during flight.

While the form of mechanism herein shown and described constitutes apreferred form of embodiment of the invention, it is to be understoodthat other forms might be adopted, all coming within the scope of theclaims which follow.

ObviouslyV What we claim is l. A fuel tank for airplanes comprising athin metal tank adapted to contain the fuel; a loose covering of rubberinclosing 2. A fuel tank for airplanes comprising i a tank of ductilemetal adapted .to contain the fuel ;l a loose cover of rubber inclosingsaid tank; and a second covering of rubber, inclosing the firstlmentionedcovering and spaced therefrom.

3.A fuel tank forairpla-nes comprising a thin ductile metal tank adaptedlto contain the fuel; a loose covering of rubber inclosing said tank;and a second covering of rubber, inclosing the first lmentioned coveringand spaced therefrom.

4. Al fuel tank for airplanes comprising a thin metal tank ladapted tocontain the fuel; a loosev covering `of rubber inclosing said tank; asecond covering of rubber inclosing the first mentioned covering andspaced therefrom; and adrain, opening through the outer covering,connecting the space between the two coverings, at its lowest points,with the atmosphere.

5. A fuel tank for airplanes'comprising a ductile metal tank adapted tocontain the fuel; .a loose covering of rubber inclosing said tank; asecond covering of rubber inclosing the firs-t mentioned covering andspaced therefrom; and a drain Vopening through the outer covering andconnecting the space between the two coverings with the atmosphere, saiddrain having its outer end positioned to prevent the escape onto theairplane of any fuel escaping therethrough.

6. A fuel tank for airplanes comprising a ductile metal tank adapted tocontain the fuel; a loose covering of rubber inclosing said tank; asecond covering of rubber inclosing the rst mentioned covering andspaced\ therefrom; and a draln opening through the outer covering andconnecting the space between the two coverings at its lowest point, withthe atmosphere, said drain terminating adJacent the owest point of thelanding gear of the airplane.

7. A fuel tank for airplanes comprising a ductile metal tank adapted tocontain the fuel; a loose covering of rubber inclosing said tank; asecond covering of rubber inclosing the first mentioned covering andspaced therefrom; .material within said space adapted to drain any fuelthat may 'escape thereon to the bottom of said space;

and a drain opening through the outer covering and connectmg said space,at its vlowest point, with the atmosphere.

- 8. In an airplane, a fuel tank, constructed to prevent leakage of fuelonto thevairplane, comprisinga metal tank adapted to contain the fuel; aloose covering of rubber inolosing said tank; a Seooncl ooveringofruhber inelosing the first mentioned covering and spaced therefrom; anda drain oonf Heating said space with the atmosphere.

9. ln an airplane, a fuel tank, oonstruoecl to prevent leakage of fuelonto the airplane, comprising a thin metal .tank adaptedL to contain thefuel; a loose covering of rubber inolosing said tank; a second coveringof ruhher inolosing the tank and spaced there from; and a drainoonneoting the space to the atmosphere, the outer enel of said drainbeing positioned to prevent the escape onto the airplane of any fuelpassing themal through.

l0.. A fuel tank for airplanes comprising a metal tank adapted tocontain the fuel; a covering inolosing saicl tank and spaoecl therefrom,hrous material Within the space between the tank and covering; and adrain through said covering connecting the space with the atmospheres.

l1. A. fuel tank for airplanes comprising a metal` tank adapted tocontain the fuel;

ineaeeo 4a rubber covering inolosing said tank and spaced therefrom,fibrous material, such as enoelsior, Withinv the space between the tankand covering; and a drain through said covering connecting the space, atits lowest point, with the atmosphere.

l2. In an airplane, a fuel tank, construotecl to prevent leakage of fuelonto the airplane, oomprising 'a tank adapted to oontain the fuel; arubber covering nolosing said tank and spaced therefrom, ibrousInaterial, suoli as excelsior, within the space between the tank andcovering; and a drain through the covering connecting4 the spaoe to theatmosphere, the outer end of said drain being positioned to prevent theescape onto the airplane of any fuel passing therethrough.

our signaln testimony whereof We alix tures.

HARRY C. MOUGEY. JAMES M. H. JACOBS. itnesses: Y

L. CLEMENTS, 'lnornas Ninerlnr, Jr.

